CN211082058U - Regulating system for preventing gas turbine from generating heat suspension - Google Patents
Regulating system for preventing gas turbine from generating heat suspension Download PDFInfo
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- CN211082058U CN211082058U CN201922158562.XU CN201922158562U CN211082058U CN 211082058 U CN211082058 U CN 211082058U CN 201922158562 U CN201922158562 U CN 201922158562U CN 211082058 U CN211082058 U CN 211082058U
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Abstract
The utility model provides a method and a regulating system which can effectively prevent the heat suspension of a gas turbine. The method comprises the following steps: s1, starting ignition of the gas turbine; s2, acquiring the current rotating speed N of the compressor in real time; real-time acquisition of current pressure P of air inlet end of air compressor1And exhaust end current pressure P2And calculating the current pressure ratio of the compressor
S3, judging whether the thermal suspension precursor occurs to the gas turbine according to the current rotating speed N or/and the current pressure ratio pi of the gas compressor, and if so, controlling and adjusting the opening of an inlet adjustable guide vane of the gas compressor until the start is completed. The adjusting system comprises a gas compressor and a controller, the gas compressor comprises a gas inlet end, an inlet adjustable guide vane, an exhaust end and a transmission shaft, the gas inlet end is provided with a gas inlet pressure sensor, the inlet adjustable guide vane is provided with a guide vane opening sensor, the exhaust end is provided with an exhaust pressure sensor, and the transmission shaft is provided with a rotating speed sensor.
Description
Technical Field
The utility model relates to a gas turbine technical field especially relates to a prevent that gas turbine from taking place governing system that heat hangs.
Background
Frequent gas turbine start-stops may be caused by a variety of reasons, such as regular maintenance, grid peak shaving, and unexpected disasters. The start-up performance of a gas turbine is of great importance to the plant, since it is not only directly related to the integrity of the gas turbine itself, but also to the economics of the overall plant operation. Therefore, ensuring safe and fast startup of the gas turbine is a great concern for the power plant owner.
If the performance of the gas compressor is reduced due to aging, scaling and the like when the gas turbine is started, the pressure cannot be normally established, so that the turbine does not work enough and the power consumption requirement of the gas compressor cannot be met, the rotating speed cannot be increased at a normal speed, a thermal suspension precursor appears, and if the thermal suspension precursor cannot be timely withdrawn, the startup overtime can cause trip; or the performance of the compressor is continuously deteriorated, so that the rotating speed is not increased any more, and heat suspension is generated; if no measures are taken to enable the combustion engine to exit from the thermal suspension state, the fuel quantity is continuously increased to enable the temperature of the outlet of the gas compressor to be continuously increased, deep thermal suspension is caused, and further the gas compressor is surged to cause serious faults. From the above analysis, it can be known that, in the starting process of the gas turbine, no matter a thermal suspension precursor occurs or a thermal suspension phenomenon occurs, the starting of the gas turbine fails, and meanwhile, the slow rise of the rotor rotation speed and the low pressure at the outlet of the compressor are important expressions that the thermal suspension is about to occur.
Currently, some power plant units are equipped with means for co-monitoring fuel quantity, rotational speed and temperature in the gas turbine system, preventing thermal suspensions from occurring by adjusting the fuel quantity. Proper fuel control is inherently important, but the ability of the compressor to establish pressure ratios during gas turbine startup is critical. Because in a fixed compressor start-up mode, the compressor performance may not meet the gas turbine co-operating requirements, no start-up failure results are recoverable regardless of fuel quantity adjustments.
SUMMERY OF THE UTILITY MODEL
In view of the above-mentioned shortcomings of the prior art, the present invention provides a method for effectively preventing heat suspension of a gas turbine.
To achieve the above object, the present invention provides a method for preventing heat hanging of a gas turbine, comprising the steps of:
s1, starting ignition of the gas turbine;
s2, acquiring the current rotating speed N of the compressor in real time; real-time acquisition of current pressure P of air inlet end of air compressor1And exhaust end current pressure P2And calculating the current pressure ratio of the compressor
S3, judging whether the thermal suspension precursor occurs to the gas turbine according to the current rotating speed N or/and the current pressure ratio pi of the gas compressor, and if so, adjusting the opening of an inlet adjustable guide vane of the gas compressor until the start is completed.
Further, the step S3 includes the following steps:
the current rotating speed N of the compressor is compared with the rotating speed N of the compressor corresponding to the preset current state0Comparing if N is less than N0And is and
if the deviation value is the set minimum rotating speed deviation value, a thermal suspension precursor is generated in the gas turbine, and the opening degree of an inlet adjustable guide vane of the gas compressor is adjusted to be increased; if N is less than N0And is and
the opening of the inlet adjustable guide vane is not changed.
Further, in the step S3, if it is determined that the detected signal is not correct
Lasting for a certain time t, and when t > t1When the temperature of the water is higher than the set temperature,t1and the opening degree of the inlet adjustable guide vane is not changed for the set system delay time.
Further, the maximum opening degree of the inlet adjustable guide vane is A, and A is a constant; in the step S3, if N is less than N0And is and
adjusting the opening degree of the inlet adjustable guide vane to increase I, wherein I is A × 0.1%, and executing the steps S2 and S3 in a circulating mode until the opening degree of the inlet adjustable guide vane is increased to I
Thermal hang precursors are eliminated.
Further, the step S3 includes the following steps:
the current pressure ratio pi of the gas compressor and the pressure ratio pi of the gas compressor corresponding to the preset current state are compared0Making comparison if pi is less than pi0And is and
if the set minimum pressure ratio deviation value is reached, a thermal suspension precursor is generated in the gas turbine, and the opening degree of an inlet adjustable guide vane of the gas compressor is adjusted to be increased; if pi < pi0And is and
the opening of the inlet adjustable guide vane is not changed.
Further, in the step S3, if it is determined that the detected signal is not correct
Lasting for a certain time t, and when t > t2When t is2And the opening degree of the inlet adjustable guide vane is not changed for the set system delay time.
Further, the maximum opening degree of the inlet adjustable guide vane is A, and A is a constant; in the step S3, if π < π0And is and
adjusting the opening degree of the inlet adjustable guide vane to increase I, wherein I is A × 0.1%, and executing the steps S2 and S3 in a circulating mode until the opening degree of the inlet adjustable guide vane is increased to I
Thermal hang precursors are eliminated.
As described above, the method according to the present invention has the following advantages:
the utility model discloses in the method, judge that gas turbine has taken place the heat and hang the precursor according to the current rotational speed of compressor, or judge that gas turbine has taken place the heat and hang the precursor according to the current pressure ratio of compressor, or when judging that gas turbine has taken place the heat and hang the precursor according to the current rotational speed of compressor and the current pressure ratio of compressor, the aperture of the adjustable stator of import through control regulation compressor promotes the pressure ratio of compressor and risees, can promote the promotion that the turbine was exerted force after the pressure ratio risees, thereby can promote the rotational speed and the pressure ratio normal rising of compressor, and effectively eliminate the heat that gas turbine takes place and hang the precursor, and then can effectively prevent that gas turbine from taking place the heat and hang.
Another object of the present invention is to provide a regulating system for preventing thermal suspension of a gas turbine.
For realizing the above-mentioned purpose, the utility model provides a prevent that gas turbine from taking place governing system that heat hangs, including compressor and controller, controller and compressor communication connection, the compressor includes inlet end, import adjustable guide vane, exhaust end and transmission shaft, the inlet end is equipped with inlet pressure sensor, be equipped with stator opening sensor on the import adjustable guide vane, the exhaust end is equipped with exhaust pressure sensor, be equipped with speed sensor on the transmission shaft, inlet pressure sensor, guide vane opening sensor, exhaust pressure sensor, speed sensor all with controller communication connection.
Further, the controller includes a pressure collection module communicatively coupled to the intake pressure sensor and the exhaust pressure sensor.
Further, the controller comprises a rotating speed collecting module which is in communication connection with the rotating speed sensor.
Further, the controller comprises an opening degree collection module which is in communication connection with the guide vane opening degree sensor.
As described above, the adjusting system for preventing heat suspension of a gas turbine according to the present invention has the following advantages:
the utility model discloses in prevent that gas turbine from taking place thermal suspension's governing system's theory of operation does: starting ignition of the gas turbine; the rotating speed sensor acquires the current rotating speed of the compressor in real time and feeds the current rotating speed back to the controller; the air inlet pressure sensor acquires the current pressure of the air inlet end of the air compressor and feeds the current pressure back to the controller, the exhaust pressure sensor acquires the current pressure of the exhaust end of the air compressor and feeds the current pressure back to the controller respectively, and the controller calculates the current pressure ratio of the air compressor according to the current pressure of the air inlet end and the current pressure of the exhaust end; the controller judges whether the gas turbine generates a heat suspension precursor according to the current rotating speed of the gas compressor, or according to the current pressure ratio of the gas compressor, or according to the current rotating speed of the gas compressor and the current pressure ratio of the gas compressor, if so, the controller controls the opening of an inlet adjustable guide vane of the gas compressor to increase, so that the pressure ratio of the gas compressor is promoted to rise, the output of the turbine is promoted to rise after the pressure ratio rises, the rotating speed and the pressure ratio of the gas compressor can be promoted to rise normally, the heat suspension precursor generated by the gas turbine is effectively eliminated, and the heat suspension of the gas turbine can be effectively prevented.
Drawings
Fig. 1 is a schematic diagram of a regulating system for preventing heat suspension of a gas turbine according to the present invention.
Fig. 2 is the utility model discloses start-up stage import adjustable stator aperture closed-loop control logic flow chart based on compressor rotational speed.
Fig. 3 is the logic flow chart of the start-up stage inlet adjustable guide vane opening closed-loop control based on the compressor pressure ratio of the utility model.
Description of the element reference numerals
1 compressor 131 exhaust pressure sensor
11-inlet adjustable guide vane 14 transmission shaft
141 rotating speed sensor of 111 guide vane opening degree sensor
12 air inlet end 15 compressor body
121 inlet air pressure sensor 2 controller
13 exhaust end 21 pressure collection module
Detailed Description
The following description is provided for illustrative purposes, and other advantages and features of the present invention will become apparent to those skilled in the art from the following detailed description.
It should be understood that the structures, ratios, sizes, etc. shown in the drawings of the present application are only used for matching with the contents disclosed in the specification, so as to be known and read by those skilled in the art, and are not used for limiting the limit conditions that the present invention can be implemented, so that the present invention has no technical essential meaning, and any modification of the structures, change of the ratio relationship or adjustment of the sizes should still fall within the scope covered by the technical contents disclosed in the present invention without affecting the function and the achievable purpose of the present invention. Meanwhile, the terms "upper", "lower", "left", "right", "middle" and "one" used in the present specification are only for convenience of description, and are not intended to limit the scope of the present invention, and the relative relationship between the terms and the modifications can be changed or adjusted without substantial technical changes and modifications.
During the start-up of the compressor 1, the inlet variable guide vanes 11 are normally kept in a fully closed or over-closed state in order to prevent surge and at the same time reduce the start-up power, but in practice the fully closed or over-closed state of the inlet variable guide vanes 11 leaves a certain margin for surge prevention at start-up. When a thermal suspension precursor occurs or the combustion engine is ready to be restarted after the startup failure caused by the thermal suspension, if the installation angle of the inlet adjustable guide vane 11 is properly reduced, namely the inlet adjustable guide vane 11 is opened, the pressure ratio of the compressor can be increased, the turbine output is increased, and the rotating speed can be normally increased. Therefore, the utility model provides a mainly adopt governing system and method of import adjustable stator, prevent that the heat from hanging taking place in the gas turbine starting process, ensure gas turbine normal start.
As shown in fig. 1 to 3, the present invention provides a method for preventing heat suspension of a gas turbine, comprising the steps of:
s1, starting ignition of the gas turbine;
s2, acquiring the current rotating speed N of the compressor 1 in real time; real-time acquisition of current pressure P at air inlet end of air compressor 11And exhaust end current pressure P2And calculating the current pressure ratio of the compressor
S3, judging whether the thermal suspension precursor occurs to the gas turbine according to the current rotating speed N or/and the current pressure ratio pi of the gas compressor 1, and if so, controlling and adjusting the opening of the inlet adjustable guide vane 11 of the gas compressor 1 until the start is completed.
The utility model discloses in the method, judge that gas turbine has taken place the heat and hang the precursor according to the current rotational speed N of compressor 1, or judge that gas turbine has taken place the heat and hang the precursor according to the current pressure ratio pi of compressor 1, or judge that gas turbine has taken place the heat and hang the precursor according to the current rotational speed N of compressor 1 and the current pressure ratio pi of compressor, through the aperture of the adjustable stator 11 of import of control regulation compressor 1, promote the pressure ratio of compressor 1 and rise, can make the promotion of turbine output after the pressure ratio risees, thereby can promote the rotational speed and the pressure ratio normal rising of compressor 1, and effectively eliminate the heat that gas turbine takes place and hang the precursor, and then can effectively prevent that gas turbine from taking place the heat and hang.
And simultaneously, as shown in fig. 1, the utility model provides a prevent that gas turbine from taking place thermal suspension's governing system, including compressor 1 and controller 2, controller 2 and 1 communication connection of compressor, compressor 1 includes inlet end 12, import adjustable stator 11, exhaust end 13 and transmission shaft 14, inlet end 12 is equipped with inlet pressure sensor 121, be equipped with stator opening sensor 111 on the import adjustable stator 11, exhaust end 13 is equipped with exhaust pressure sensor 131, be equipped with speed sensor 141 on the transmission shaft 14, inlet pressure sensor 121, stator opening sensor 111, exhaust pressure sensor 131, speed sensor 141 all with 2 communication connection of controller. The utility model discloses in prevent that gas turbine from taking place thermal suspension's governing system's theory of operation does: starting ignition of the gas turbine; the rotating speed sensor 141 collects the current rotating speed of the compressor 1 in real time and feeds the current rotating speed back to the controller 2; the air inlet pressure sensor 121 acquires the current pressure of the air inlet end of the air compressor 1 and feeds the current pressure back to the controller 2, the exhaust pressure sensor 131 acquires the current pressure of the exhaust end of the air compressor 1 and feeds the current pressure back to the controller 2 respectively, and the controller 2 calculates the current pressure ratio of the air compressor according to the current pressure of the air inlet end and the current pressure of the exhaust end; the controller 2 judges whether the gas turbine generates a heat suspension precursor according to the current rotating speed of the gas compressor 1, or according to the current pressure ratio of the gas compressor, or according to the current rotating speed of the gas compressor 1 and the current pressure ratio of the gas compressor, if so, the controller 2 controls the opening of the inlet adjustable guide vane 11 of the gas compressor 1 to increase, so that the pressure ratio of the gas compressor 1 is promoted to be increased, the output of the turbine is promoted to be increased after the pressure ratio is increased, the normal increase of the rotating speed and the pressure ratio of the gas compressor 1 can be promoted, the heat suspension precursor generated by the gas turbine can be effectively eliminated, and the heat suspension of the gas turbine can be effectively prevented.
Example one
As shown in fig. 1 and 2, step S3 of the present embodiment includes the steps of:
the current rotating speed N of the compressor 1 and the rotating speed N of the compressor corresponding to the preset current state are compared0Comparing if N is less than N0And is and
adjusting the inlet of the compressor 1 to a set minimum deviation value of the rotating speed when a thermal suspension precursor is generated in the gas turbineThe opening degree of the opening-adjustable guide vanes 11 is increased; if N is less than N0And is and
the opening of the inlet adjustable guide vanes 11 is not changed.
In step S3 of the present embodiment, if
Lasting for a certain time t, and when t > t1When t is1For a set system delay time, the opening of the inlet adjustable guide vane 11 is not changed.
As shown in fig. 1 and fig. 2, the maximum opening degree of the inlet adjustable guide vane 11 in the present embodiment is a, and a is a constant; in step S3, if N is less than N0And is and
the opening degree of the inlet adjustable guide vane 11 is adjusted to be increased by I, and I is equal to a × 0.1%, and steps S2 and S3 are executed in a loop until the opening degree is increased by I
Thermal hang precursors are eliminated.
The adjusting system is used for realizing the method for preventing the thermal suspension of the gas turbine, namely the adjusting system is used for realizing the method for preventing the thermal suspension of the gas turbine. In other embodiments, the regulation system may also be implemented to remove the precursor to thermal hang-up of the gas turbine and prevent thermal hang-up of the gas turbine by other methods of operation.
As shown in fig. 1, the controller 2 of the present embodiment includes a pressure collection module 21, and the pressure collection module 21 is connected in communication with an intake pressure sensor 121 and an exhaust pressure sensor 131. In the above step S2, the intake pressure sensor 121 acquires the current pressure P at the intake end of the compressor 11And then P is mixed1Feeds back to the pressure collection module 21, and the exhaust pressure sensor 131 collects the current pressure P of the exhaust end of the compressor 12And then P is mixed2The feedback is sent to the pressure collection module 21, and the controller 2 obtains the air inlet end through the pressure collection module 21Front pressure P1And exhaust end current pressure P2And calculating the current pressure ratio of the compressor
The controller 2 in this embodiment includes a rotation speed collecting module, and the rotation speed collecting module is in communication connection with the rotation speed sensor 141. In the step S2, the rotation speed sensor 141 acquires the current rotation speed N of the compressor 1 in real time and feeds back N to the rotation speed collection module, and the controller 2 obtains the current rotation speed N of the compressor 1 through the rotation speed collection module.
The controller 2 in this embodiment includes an opening degree collection module, and the opening degree collection module is connected to the guide vane opening degree sensor 111 in communication. In the step S2, the guide vane opening sensor 111 collects the current opening of the inlet adjustable guide vane 11 in real time and feeds the current opening back to the opening collection module, and the controller 2 obtains the current opening of the inlet adjustable guide vane 11 through the opening collection module.
In the above step S3 of this embodiment, the controller 2 compares the current speed N of the compressor 1 with the preset compressor speed N corresponding to the current state0Comparing if N is less than N0And is and
the thermal suspension precursor of the gas turbine occurs, the controller 2 adjusts the opening degree of the inlet adjustable guide vane 11 of the compressor 1 to increase by I, and I is a × 0.1%, and the steps S2 and S3 are executed in a circulating manner until the thermal suspension precursor occurs
At the moment, the thermal suspension precursor is eliminated, namely the gas turbine exits the thermal suspension precursor state; if N is less than N0And is and
lasting for a certain time t, and when t > t1When t is1For a set system delay time, the controller 2 controls the opening degree of the inlet adjustable guide vane 11 to be unchanged, that is, the controller 2 exits the control mode for adjusting the opening degree of the inlet adjustable guide vane 11 to be increased.
The adjusting system and method in this embodiment may be specifically referred to as an adjusting system and method for preventing the gas turbine from generating thermal suspension during the starting process by using the inlet adjustable guide vane, and the adjusting system and method changes the state of the gas compressor 1 by adjusting the opening degree of the inlet adjustable guide vane 11 according to the performance rule of the gas compressor 1 during the starting process, thereby finally achieving the technical effect of preventing the gas turbine from generating thermal suspension during the starting process.
In this embodiment, the controller 2 is in communication connection with the inlet adjustable guide vane 11, and the controller 2 can control the opening of the inlet adjustable guide vane 11 to increase or decrease.
The compressor 1 is also referred to as compressor unit in this embodiment. And the compressor 1 comprises a compressor body 15 and a transmission device comprising the transmission shaft 14. In this embodiment, the range of the opening degree indicator H of the inlet adjustable guide vane 11 is between a% and b%, wherein-20 is equal to or greater than a and equal to or less than 0, and 100 is equal to or greater than b and equal to or less than 120, wherein a smaller value of the opening degree indicator H indicates that the inlet adjustable guide vane 11 of the compressor 1 is closed, and a larger value of the opening degree indicator H indicates that the inlet adjustable guide vane 11 of the compressor 1 is opened.
In this embodiment, the controller 2 includes a closed-loop control mode of the opening of the inlet adjustable guide vane at the start-up stage based on the rotation speed of the compressor. The above steps S1 to S3 of the present embodiment are also referred to as a closed-loop control mode of the inlet adjustable guide vane opening degree during the start-up phase based on the compressor rotation speed. After the gas turbine is successfully ignited by starting, the controller 2 enters a closed-loop control mode of the opening degree of the inlet adjustable guide vane at the starting stage based on the rotation speed of the compressor, so as to execute the steps S2 and S3. T above1A preset system delay time for the controller 2 to determine the current speed N of the compressor 1 and the speed N of the compressor corresponding to the preset current state0Whether the difference is in steady state, rather than fluctuating randomly.
In the embodiment, after the opening degree of the inlet adjustable guide vane 11 is increased, the current rotating speed N of the compressor 1 and the rotating speed N of the compressor corresponding to the preset current state are judged in the closed-loop control mode0The deviation therebetween. If the difference between the measured value and the set value is still larger than the minimum deviation, the gas turbine is judged to be still in the thermal suspension precursor state, and the controller 2 enters the starting based on the rotating speed of the compressorAnd in the dynamic stage inlet adjustable guide vane opening closed-loop control mode, the opening of the inlet adjustable guide vane 11 of the compressor 1 is continuously increased by 0.1 percent of span until the difference value between the measured value and the set value is less than the minimum deviation, and the thermal suspension precursor state is exited.
Example two
As shown in fig. 1 and 3, step S3 of the present embodiment includes the following steps:
the current pressure ratio pi of the gas compressor and the pressure ratio pi of the gas compressor corresponding to the preset current state are compared0Making comparison if pi is less than pi0And is and
if the minimum pressure ratio deviation value is set, a thermal suspension precursor is generated in the gas turbine, and the opening degree of an inlet adjustable guide vane 11 of the gas compressor 1 is adjusted to be increased; if pi < pi0And is and
the opening of the inlet adjustable guide vanes 11 is not changed.
In step S3 of the present embodiment, if
Lasting for a certain time t, and when t > t2When t is2For a set system delay time, the opening of the inlet adjustable guide vane 11 is not changed.
As shown in fig. 3, in the present embodiment, the maximum opening degree of the inlet adjustable guide vane 11 is a, and a is a constant; in the step S3, if π < π0And is and
the opening degree of the inlet adjustable guide vane 11 is adjusted to be increased by I, and I is equal to a × 0.1%, and steps S2 and S3 are executed in a loop until the opening degree is increased by I
The hot-hang precursor being eliminated, i.e. gas turbine backingAnd generating a thermal suspension precursor state.
The adjusting system is used for realizing the method for preventing the thermal suspension of the gas turbine, namely the adjusting system is used for realizing the method for preventing the thermal suspension of the gas turbine. In other embodiments, the regulation system may also be implemented to remove the precursor to thermal hang-up of the gas turbine and prevent thermal hang-up of the gas turbine by other methods of operation.
As shown in fig. 1, the controller 2 of the present embodiment includes a pressure collection module 21, and the pressure collection module 21 is connected in communication with an intake pressure sensor 121 and an exhaust pressure sensor 131. In the above step S2, the intake pressure sensor 121 acquires the current pressure P at the intake end of the compressor 11And then P is mixed1Feeds back to the pressure collection module 21, and the exhaust pressure sensor 131 collects the current pressure P of the exhaust end of the compressor 12And then P is mixed2The current pressure P of the air inlet end is obtained by the controller 2 through the pressure collecting module 21 by feeding back to the pressure collecting module 211And exhaust end current pressure P2And calculating the current pressure ratio of the compressor
The controller 2 in this embodiment includes a rotation speed collecting module, and the rotation speed collecting module is in communication connection with the rotation speed sensor 141. In the step S2, the rotation speed sensor 141 acquires the current rotation speed N of the compressor 1 in real time and feeds back N to the rotation speed collection module, and the controller 2 obtains the current rotation speed N of the compressor 1 through the rotation speed collection module.
The controller 2 in this embodiment includes an opening degree collection module, and the opening degree collection module is connected to the guide vane opening degree sensor 111 in communication. In the step S2, the guide vane opening sensor 111 collects the current opening of the inlet adjustable guide vane 11 in real time and feeds the current opening back to the opening collection module, and the controller 2 obtains the current opening of the inlet adjustable guide vane 11 through the opening collection module.
In the above step S3 of this embodiment, the controller 2 compares the compressor current pressure ratio pi with the compressor pressure ratio pi corresponding to the preset current state0Making comparison if pi is less than pi0And is and
a thermal suspension precursor occurs in the gas turbine, the controller 2 adjusts the opening degree of the inlet adjustable guide vane 11 to increase by I, which is a × 0.1%, and the steps S2 and S3 are executed in a loop until the thermal suspension precursor occurs in the gas turbine
At the moment, the thermal suspension precursor is eliminated, namely the gas turbine exits the thermal suspension precursor state; if pi < pi0And is and
lasting for a certain time t, when t > t2In the meantime, the controller 2 controls the opening degree of the inlet adjustable guide vane 11 to be unchanged, that is, the controller 2 exits the control mode of adjusting the opening degree of the inlet adjustable guide vane 11 to be increased.
The adjusting system and method in this embodiment may be specifically referred to as an adjusting system and method for preventing the gas turbine from generating thermal suspension during the starting process by using the inlet adjustable guide vane, and the adjusting system and method changes the state of the gas compressor 1 by adjusting the opening degree of the inlet adjustable guide vane 11 according to the performance rule of the gas compressor 1 during the starting process, thereby finally achieving the technical effect of preventing the gas turbine from generating thermal suspension during the starting process.
In this embodiment, the controller 2 is in communication connection with the inlet adjustable guide vane 11, and the controller 2 can control the opening of the inlet adjustable guide vane 11 to increase or decrease.
The compressor 1 is also referred to as compressor unit in this embodiment. And the compressor 1 comprises a compressor body 15 and a transmission device comprising the transmission shaft 14. In this embodiment, the range of the opening degree indicator H of the inlet adjustable guide vane 11 is between a% and b%, wherein-20 is equal to or greater than a and equal to or less than 0, and 100 is equal to or greater than b and equal to or less than 120, wherein a smaller value of the opening degree indicator H indicates that the inlet adjustable guide vane 11 of the compressor 1 is closed, and a larger value of the opening degree indicator H indicates that the inlet adjustable guide vane 11 of the compressor 1 is opened.
In this embodiment, the controller 2 includes a closed-loop control mode of the inlet adjustable guide vane opening at the start-up stage based on the compressor pressure ratio. The above steps S1 to S of the present embodiment3 is also called a starting stage inlet adjustable guide vane opening degree closed-loop control mode based on the pressure ratio of the compressor. After the gas turbine is successfully ignited at the start, the controller 2 enters the inlet adjustable guide vane opening closed-loop control mode at the start stage based on the compressor pressure ratio, so as to execute the above steps S2 and S3. T above2A system delay time preset for the controller 2 is used for judging the current pressure ratio pi of the compressor and the pressure ratio pi of the compressor corresponding to the preset current state0Whether the difference is in steady state, rather than fluctuating randomly.
In the embodiment, after the opening degree of the inlet adjustable guide vane 11 is increased, the method judges the current pressure ratio pi of the compressor and the pressure ratio pi of the compressor corresponding to the preset current state in the closed-loop control mode0The deviation therebetween. If the difference between the measured value and the set value is still larger than the minimum deviation, the gas turbine is judged to be still in the thermal suspension precursor state, the controller 2 enters a closed-loop control mode of the opening degree of the inlet adjustable guide vane at the starting stage based on the pressure ratio of the gas compressor, the opening degree of the inlet adjustable guide vane 11 of the gas compressor 1 is continuously increased by 0.1% of span until the difference between the measured value and the set value is smaller than the minimum deviation, and the thermal suspension precursor state is exited.
The utility model discloses in gas turbine starting process, through current rotational speed N of real-time supervision compressor 1, the current pressure P of inlet end of compressor 11And exhaust end current pressure P2And the thermal suspension is judged to be about to occur by combining the change rule of related parameters in the normal starting process, and the opening of the inlet adjustable guide vane 11 of the large gas compressor 1 is opened to prevent the thermal suspension from occurring, so that the combustion engine is started successfully, the economic loss of a power plant is recovered, and the service life damage of the combustion engine caused by trip due to the starting failure is also avoided.
To sum up, the utility model discloses various shortcomings in the prior art have effectively been overcome and high industry value has.
The above embodiments are merely illustrative of the principles and effects of the present invention, and are not to be construed as limiting the invention. Modifications and variations can be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which may be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.
Claims (4)
1. The utility model provides a prevent that gas turbine from taking place governing system that heat hangs, includes compressor (1) and controller (2), controller (2) and compressor (1) communication connection, a serial communication port, compressor (1) includes inlet end (12), import adjustable guide vane (11), exhaust end (13) and transmission shaft (14), inlet end (12) are equipped with inlet pressure sensor (121), be equipped with guide vane opening sensor (111) on import adjustable guide vane (11), exhaust end (13) are equipped with exhaust pressure sensor (131), be equipped with speed sensor (141) on transmission shaft (14), inlet pressure sensor (121), guide vane opening sensor (111), exhaust pressure sensor (131), speed sensor (141) all with controller (2) communication connection.
2. The regulating system for preventing thermal suspension of a gas turbine according to claim 1, wherein the controller (2) comprises a pressure collection module (21), the pressure collection module (21) being communicatively connected to an intake pressure sensor (121) and an exhaust pressure sensor (131).
3. The regulation system for preventing heat suspension of a gas turbine according to claim 1, wherein the controller (2) comprises a rotational speed collection module, which is communicatively connected to a rotational speed sensor (141).
4. The regulating system for preventing thermal suspension of a gas turbine according to claim 1, wherein the controller (2) comprises an opening degree collecting module, which is communicatively connected with a guide vane opening degree sensor (111).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201922158562.XU CN211082058U (en) | 2019-12-05 | 2019-12-05 | Regulating system for preventing gas turbine from generating heat suspension |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922158562.XU CN211082058U (en) | 2019-12-05 | 2019-12-05 | Regulating system for preventing gas turbine from generating heat suspension |
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| CN211082058U true CN211082058U (en) | 2020-07-24 |
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| CN201922158562.XU Active CN211082058U (en) | 2019-12-05 | 2019-12-05 | Regulating system for preventing gas turbine from generating heat suspension |
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